Airplane bomb



NOV. 24, s H EMERY I AIRPLANE BOMB Filed July 12, 1940 INVENTOR. STANLEY H. EMERY ATTORN Patented Nov. 24, 1942 UNITED 2 Claims.

This invention relates to airplane bombs.

The general object of the invention is to provide a novel airplane bomb which explodes a predetermined distance below the releasing airplane.

A more specific object of the invention is to provide a novel airplane time bomb wherein the time of explosion may be controlled from within the releasing airplane.

Another object of the invention is to provide a novel air plane time bomb having improved safety devices included therein.

Another object of the invention is to provide a novel airplane bomb particularly adapted to be released from an airplane in combat against enemy aircraft therebelow.

Other objects and the advantages of this invention will be apparent from the following description taken in connection with the accompanying drawing, wherein:

Fig. 1 is a fragmentary view of an airplane with my improved airplane bomb and time control means therefor mounted thereon;

Fig. 2 is a central sectional view of the bomb, partly in elevation;

Fig. 3 is an enlarged fragmentary sectional view taken on line 33, Fig. 2;

Fig. 4 is a fragmentary sectional view taken on' line 44, Fig. 2;

Fig. 5 is an enlarged fragmentary sectional view taken on line 5-5, Fig. 2; and

Fig. 6 is an enlarged front view of the control means shown in Fig. 1.

Referring to the drawing by reference characters I have shown my invention as embodied in a novel airplane bomb which is indicated generally at H]. As shown in Fig. l the bomb Ill may be carried in the bomb rack I l of a bombing airplane l2. The airplane 12 includes an instrument panel [3 upon which may be mounted the time control device to be later described.

As shown in Fig. 2 the bomb includes a lower hollow cylindrical body portion l4 having explosive material l therein and having a detonating member it, which may include a primer and a booster, in the upper wall 1 thereof. A hollow streamline tail portion I8 is secured to the body portion [4 as by threads 13 and includes external guiding fins 2|].

A bracket 2| within the tail portion l8 supports a clockwork mechanism 22. The mechanism 22 includes a central output shaft 23 shown as coaxial with the bomb. At its upper end the shaft 23 extends through an aperture 24 in the socket member 25 having a square sectioned bore 26 therein.

A disk 21 is secured to the lower end of the shaft 23. As shown in Fig. 3, the disk 21 is substantially circular but has a removed portion forming an arcuate contour 28 in the periphery thereof.

An arm 29 is pivoted to the shell H] as at 33 and includes a roller 3| mounted on the end thereof and engaging the periphery of the disk 21.

A hammer member 32 is pivoted to a bracket 33 which is secured to the shell IS. The hammer member 32 includes an'extending portion 34 in line with the detonating member [6 and further includes a lug 35 urged into engagement with the arm 29 by a spring 36. The arm 29 thus holds the hammer from striking the detonating member.

The gear train of the clockwork mechanism 22 includes a spur gear 31 which may be engaged by a dog 38 pivoted to the bracket 2|. When the bomb [0 is mounted in the rack I I, an extending portion 39 of the rack engages a slidable pin 40 which is mounted in a fixture 4| on the tail portion l8. The pin 40 engages the dog 38 and. urges the latter into engagement with the spur gear 31. When the bomb is released (in a manner to be later described) the pin 40 is urged outwardly by a spring 42 thus releasing the dog 38.

A safety pin 43 at one end extends through the tail portion l8 and at the other end is screwed into the wall I! as at 44. The pin 43 engages the dog 38 and a projection 44' on the arm 29 as shown in Fig. 3 so that these parts are rendered inoperative when the pin 43 is in position.

The position of the disk 21 relative to the arm 29 may be controlled from within the airplane through a time control indicator device 50 mounted upon the instrument panel l3. The device 50 includes a pointer 5| rotatable over a dial 52 including indicia 53 indicating the distance below the releasing airplane that the bomb will explode. The pointer 5| is secured to one end of a flexible shaft 54 the other end of which terminates in a square portion 58 which slidably and removably engages in the bore 26 as shown in Fig. 5. The shaft 54 is encased in a flexible tube 53. The end of the tube 56 includes a collar 51 which is recessed at to fit over a reduced end portion 59 on the socket member 25.

During manufacture the clockwork mechanism 22 is installed in the bomb in wound or loaded condition and is prevented from unwinding by end of the tail portion [8 and terminates in a 55 the pin 43 which engages the dog 38. the latter in turn engaging the gear 31. in position during storage.

When the bomb is installed in the rack II the portion 39 holds the pin 40 in engagement with the dog 38. The pin 43 may then be removed and thereafter the mechanism is held in locked position through the pin 40. The member 58 is then inserted into the socket 25.

When it is desired to use the bomb, as upon enemy aircraft, the operator determines the distance between his own plane and the aircraft he wishes to destroy. The pointer 5| is then set to the corresponding distance on the dial 52. 'It

Ihe pin 43 is left will be readily apparent that this controls the position of the disk 21 relative to the arm 29. The bomb is then released from the rack in the usual manner. The portion 55 disengages from the socket 25 allowing the bomb to fall freely. As the bomb is released the pin 40 releases the dog 33 from engagement with the gear 31. This allows the mechanism 22 to rotate the disk 21. When the arcuate portion 28 approaches the roller 3!, the arm 29 is allowed to rotate about its pivot thus releasing the hammer member. The extending portion of the hammer strikes the detonating member IS which causes the bomb to explode.

From the foregoing description it will be apparent that I have invented a novel airplane bomb that is highly effective for its intended purpose.

Having thus described my invention, I claim:

1. In an airplane bomb construction, a support. a bomb on said support, said bomb including a hollow body having an explosive therein, a detonating member in said body, a firing hammer for said detonating member, a clockwork mechanism having a time setting shaft, a disk on one end of said shaft, said disk being substantially circular and having an arcuate notched portion in the periphery thereof, a pivoted arm on said body, said arm having a, roller mounted on the end thereof, said roller engaging the periphery of said disk, a lug on said hammer, said arm engaging said lug to hold said hammer in a safety position when said roller engages said circular portion of said disk but releasing said hammer when said roller engages the notched portion of said disk, said time setting shaft extending beyond said bomb, a flexible shaft removably engaging the outer end of said time setting shaft, and an indicator member associated with the other end of said flexible shaft, the position of said disk relative to said arm being determined by the position of said indicator member.

2. In a bomb, a body including a time controlled cletonating device, means to control the operation of the detonating device, said control means including a pivoted dog, a pin slidable on the body and normally disposed in the path of the dog, a second pin slidable on the body in the path'of the dog, said second pin protruding from the body and adapted to engage a, portion of a bomb rack to normally hold the second pin in dog-engaging position, said first pin being retractable from engagement with the dog.

STANLEY H. EMERY. 

